Automatic stabilizer for aeroplanes.



E. YEAMANS. .11110111.1110 STABILIZER POR AEROPLANES.

y 111211101111011 FILED M1116, 1911. 1,040,089. Patented Oct. 1, 1912 2 SHEETS-SHEET 1.

@vivente/r, lyeejeawva/ @vih/105Mo E. YEAMANS. AUTOMATIC STABILIZER POR ,AEROPLANE APPLIOATION FILED DEO. 16, 1911.

Patented 001.1,1912

2 SHEETS-SHEET 2.

EUGENE YEAMANS, oF

`CQLLEGEPORT,l TEXAS.

AUTOMATIC STA-BILIZER FOR AEROPLANES.

`Specication of Iietters Patent.

Patented oct. 1 1912.

Application led December 16, 1911. Serial No. 666,085.

To all whom 'it may concern:

Beit known that I, EUGENE YEAMANS, a citizen of the United States, residing at Collegeport, in the county of Metagorda and State of Texas, have invented new and useful Improvements in Automatic Stabilizers for Aeroplanes, of which the following is a specification.

This invention relates to an autcmatlc stabilizer for aeroplanes or flying machines of the heavier-than-air class, the object of the invention being to provide simple, reliable and effective gyroscopically-controlled means for correcting any tendency of the machine to' tilt unduly on its longitudinal axis, whereby lateral stabilit-y will be automatically maintained.

The invention consists of the features of construction, combination and arrangement of parts, hereinafter fully described and claimed, reference being had to the accompanying drawings, in which Figure l is a front elevation of a monoplane embodying my invention. Fig. 2 is a side elevation of the same. Fig. 3- is a longitudinal section on line 3 3 of Fig. 1. ig. 4 is a transverse section on line 4-4 of Fig. 2.

In the illustrated exemplifcation of my invention, I have shown the application of the same to a flying machine of the monolplane type, although it is to be understood that it may be applied tofbiplanes or other types of flying machines. It will also be understood that while the invention is shown for maintaining lateral control, the gyroscopic device may be arranged to coperate with one or more horizontal rudders or balancing devices for maintaining longitudinal control.

Referring .to the drawings, `1 designates the main frame of the machine, and 2 and 3 the wings forming the supporting surface thereof, which wings are respectively provided with warpable tips or portions 4 and 5, or balancing devices for lateral control. Any equivalents of these wing tips may be employed. A motor 6, herein shown as of the rotary body type, is suitably supported at the frontof the main frame, and to the shaft 7 of said motor is connected a propeller 8. To the rotary body of this motor is connected a shaft 9, in gear with an elec- ;ric generator 10 (dynamo or high tenslon nagnets) whereby said generator 1s driven.

nupported on the frame is a bearing block y.in contact with the 11 stayed by. braces 12 and provided with a v socket 13 in which fits a ball or spherical head 14 formed with a bearingcavity 15 in which are antifriction bearing members 16. This ball is provided with notches 17 engaged by retaining members 18, whereby the ball is permitted to turn or oscillate in a` lateral direction only. These retaining members are secured to the block by screws or bolts 19, which also serve as binding posts. Arranged above rthe ball and socket members 11 and 14 is a normally horizontal casing 20 having tubular top and bottom extensions-21 and 22. n In said casing is disposed a 4gyroscope wheel 23 fixed to a vertical shaft .24, the lower end of which is mounted for rotation in the cavity 15 and bearing members 16. The upper end of the shaft is inclosed in the tube 21 and formed with a conical ,recess 25 recelvlng a conlcal bearing member 26 lcarried by a stem 27 which projects outward through the upper end of said tube 21 and carries a cross piece or head 28. Cords or cables 29 connect the ends of said head or cross piece with the balancin devices 4 and 5, to eilect anautomatic a justment in opposite directions when the machine tilts laterally in either direction. The tube 21 of the gyroscope casing is coupled to the ballor head 14 by the casing and ields of an electric motor 340, the armature 31 of which is mounted on the shaft 24, whereby said shaft and the .gyro-scope wheel are adapted to be driven. Conductors 32 connect the motor fields with the generator 10, through which current is .supplied to the -motor in the operation of the apparatus.

The gyroscope device is adapted for maintaining t-he lateral balance of the machine under ordinary conditions of service, and it will be understood from the foregoing description that when the machine is laterally balanced the shaft 24 will be` at right angles or perpendicular to any certain normally horizontal portion of the machine structure, whereby the balancing devices 4 and 5 will be positioned at equal distances from the said shaft 2.4,` so that they will be retained in their normal position to adapt themachine to move in a straight horizontal course. When, however, the machine tilts laterally in either direction, a relative angu lar motion between the machine structure and the gyroscope and its shaft 24 will be established through the movement of the machine about the ball and socket connection, whereby one of the cables 29 willbeslackened and the other drawn upon to release one of the balancing devices for up- Ward deflection to decrease its angle' of in-` oidence under the action of the air and pull `down the other balancing device to increase its angle of incidence. vices will thereby be adjusted to restore the machine to a normal balance, and when the machine is again laterally balanced the parts will have the relative normal positionhereinbefore described, in which the balancing devices are maintained at the same angle of incidence by the gyroscopic device. Thus when the machine is in flight the balancing devices will be controlled automatically to maintain the lateral balance or equilibrium, as will be readily understood.

Any suitable means may be providedfor ythrowing the gyroscope device outtofaction when desired. Having thus described the invention, what I claim as new is:

In a flying machine, the combination, with l a gliding structure provided with lateral balancing elements, of a bearing member on said gliding structure, -a bearing ball mounted to tilt laterally in said bearing member, a vertical shaft journaled at its lower end in the ball and provided at its upper end with a bearing socket, a gyroscope wheel. carried by said shaft, a casing inclosing the` upper .portion of the shaft and having an expanded portion inclosing said gyroscope wheel, an elect-ric motor having its armature mounted on said shaft and its fields inclosed Within a casing connecting the lower end of the first-named casing with the ball, a head or cross piece, a conical bearing member connecting the upper end ofthe first-named casing with said crossfpiece and engaging v the bearing recess in the shaft, and connections between said head and cross pieces and the balancing elements.

In testimony whereof I aiix my signature in presence of two witnesses.

EUGENE YEAMANS.

Witnesses:

Gr. M. MAGILL, G. S. HU'roHINsoN. 

